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Fatigue Life of Wing Components for Civil Aircraft

Published online by Cambridge University Press:  28 July 2016

Keri Williams
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Extract

In the past attempts have been made to correlate the estimated load variations which the component will experience during a stipulated lifetime (in hours) with estimations of the fatigue strength (in cycles of loading) for typical structural components, such as wing spar boom joints, riveted joints, and so on. The trend of thinking so far has been that one should design for a certain fatigue life. In this paper it is shown that, even with the most careful attention given to the detail design of aluminium alloy components, it is not possible to attain what has been regarded hitherto as the minimum acceptable fatigue strength for typical structures, i.e. 2 x 106 cycles of 1g±7½ per cent. ultimate strength of the structure, based on present British Civil Airworthiness Requirements (Reserve Factor 1.0). There is no implied criticism of the criterion which is an ideal one, and if structures attained the criterion then the fatigue life would be adequate.

Type
Research Article
Information
The Aeronautical Journal , Volume 56 , Issue 503 , November 1952 , pp. 842 - 848
Copyright
Copyright © Royal Aeronautical Society 1952

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References

1. Fisher, W. A. P. A Comparison of the Endurance of Various Aircraft Structures under Fluctuating Loading. Unpublished Ministry of Supply Report.Google Scholar
2. Pollicutt, F. H. (1949). Contribution to Discussion (Fatigue Resistance of Extruded Z-section Stringers in Aluminium Alloy to Specification D.T.D.364). Journal of the Royal Aeronautical Society, August 1949, p. 782.Google Scholar
3. Lundberg, B. K. O. and Wallgren, C. G. E. (1949). A Study of Some Factors Affecting the Fatigue Life of Aircraft Parts with Application to Structural Elements of 24S-T and 75S-T Aluminium Alloys. (Flygtekniska Försöksanstalten (F.F.A.) Report No. 30, 1949.Google Scholar
4. Starkey, R. Review pf Gust Data from Civil Aircraft V-g Records. Unpublished Ministry of Supply Report.Google Scholar
5. Taylor, J. Design and Use of Counting Accelerometers. Unpublished Ministry of Supply Report.Google Scholar
6. Rhode, R. and Donely, P. (1944). Frequency of Occurrence of Atmospheric Gusts and of Related Loads on Airplane Structures. N.A.C.A. A.R.R. Report No. L.4121, November 1944.Google Scholar
7. Hislop, G. S. (1951). Clear Air Turbulence over Europe. The Journal of the Royal Aeronautical Society, April 1951.Google Scholar
8. Miner, M. A. (1945). Cumulative Damage in Fatigue. Journal of Applied Mechanics, Vol. 12, No. 3, 1945.Google Scholar